• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.5
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• pp.375-384
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• 2012

This paper presents numerical results comparing the performance of the 2008 Wilcox $\mathcal{k}-{\omega}$ turbulence model to the one of the 1988 Wilcox $\mathcal{k}-{\omega}$ model for supersonic flows. A comparison with experimental data is offered for a shock wave/turbulent boundary layer interaction case and two ramp injector mixing cases. Furthermore, a comparison is performed with empirical correlations on the basis of skin friction for flow over a flat plate and shear layer growth for a free shear layer. It is found that the maximum injectant mass fraction of some ramp injector cases is better predicted using the 1988 Wilcox model. On the other hand, the 2008 model performs better in simulating shock-boundary layer cases.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.4
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• pp.281-286
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• 2007

The Navier-Stokes equations are numerically solved for a two-dimensional small nozzle with the area ratio of 1.8 between the throat and the exit. The shock structures are verified inside the nozzle and near the exit varying with the pressure ratio and the length of the diverging part, respectively. Especially the irregular patterns in the pressure distribution near the throat are analyzed based on the geometric characteristics. It is found that there are similar phenomena in the shock wave structure between the pressure ratio and the length changes. Also there exists a normal shock just between two different oblique shocks crossing each other in special cases.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.21 no.1
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• pp.174-184
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• 1997

A shock wave, being an irreversible process, gives rise to entropy increase. A great deal of effort has been made to control shock wave and boundary layer interaction related to energy losses as well as problems of vibration and noise. In the present study, tests are performed on a roof mounted half circular arc in an indraft type supersonic wind tunnel to evaluate the effects of porosity, length and depth of cavity in passive control of shock wave on the attenuation of shock strength by reviewing the measured static pressures at the porous wall and cavity. Also the flow field is visualized by a Schlieren system. The results show that in the present study the porosity of 8% produced the largest reduction of pressure fluctuations and that for the same porosity, the strength of shock wave decreases with the increasings of the depth and length of cavity.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.6
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• pp.9-16
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• 2010

The SFRJ(Solid Fuel Ram-Jet) propulsion is attractive for projectiles because of the combination of high propulsive performance and low system complexity more than conventional projectiles. The Objective of this research was to characterize the inlet aerodynamic characteristics (center-body & pitot type) in SFRJ. Diffuser static pressure & combustion chamber pressure was tested and the AoA was changed $0^{\circ}$ and $4^{\circ}$ at Mach number of 3.0 for performance estimate. The performance study of inlet was carried out with the Schlieren system and Supersonic cold-flow system. Under mach 3.0, the center-body showed twice higher total pressure recovering ratio than the pitot type. A Computational fluid dynamic solution is applied internal flow of inlet and the solutions are compared with experimental results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.123-127
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• 2009

The purpose of this research is to investigate the dynamic characteristics of fluidic thrust vector control using the co-flow injection. In previous research, both numerical and experimental approaches for steady state were conducted to investigate operation-parameters and detail flow structure of the fluidic thrust vector control system. Based upon the previous results, numerical unsteady calculation was conducted to analyze the dynamic characteristics of jet up- and down-ward vectoring so that the transition time and the pressure distribution along the wall, and so on were investigated.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.4
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• pp.1-10
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• 2006

Separation motion analysis of staging system is conducted using combined analysis programs, which include unsteady aerodynamic analysis codes and dynamic motion analysis tools. In this study, the analysis is for the long-rang missile staging system. The purpose of this study is to verify the safety and reliance of the proposed staging system, and to find out the influence of angle of attack perturbation on staging. A structured parallel overset mesh called Chimera grid is used for the simulation of unsteady supersonic Euler flow solver. In addition, unsteady dynamic simulations are also performed.

• Journal of the Korean Society of Industry Convergence
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• v.2 no.2
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• pp.115-124
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• 1999

The interaction of weak normal shock wave with turbulent boundary layer in a supersonic nozzle was investigated experimentally by wall static pressure measurements and by schlieren optical observations. The lime-mean flow in the interaction region was classified into four patterns according to the ratio of the pressure $p_k$ at the first kink point in the pressure distribution of the interaction region to the pressure $p_1$ just upstream of the shock. It is shown for any flow pattern that the wall static pressure rise near the shock foot can be described by the "free interaction" which is defined by Chapman et al. The ratio of the triple point height $h_t$ of the bifurcated shock to the undisturbed boundary layer thickness ${\delta}_1$ upstream of the interaction increases with the upstream Mach number $M_1$, and for a fixed $M_1$, the normalized triple point height $h_t/{\delta}_1$ decreases with increasing ${\delta}_1/h$, where h is the duct half-height.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.6
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• pp.463-467
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• 2016

In this paper, acceleration and pressure exerted on a human model were measured under a supersonic condition in a shock tunnel. In order to measure these in an interference-free environment, free-fall technique with an electromagnet and a three-dimensional iron-powdered human model was used. Free-fall experiment was conducted at Mach 4 and the force acting on the model was obtained by calculating the displacement from the flow visualization images.

• Proceedings of the Materials Research Society of Korea Conference
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• 2009.05a
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• pp.37.2-37.2
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• 2009

다이렉트 프린팅 방식에 대한 수요가 높아지면서 마이크로 노즐에 대한 수요도 높아지고 있다. 마이크로 노즐은 Nano particle deposition system (NPDS)에서 가장 중요한 부분으로 금속이나 세라믹 분말을 음속으로 가속시키는 역할을 한다. 또한 마이크로 노즐은 마이크로 스페이스 셔틀과 주사바늘이 없는 약물 주사 시스템 등의 많은 분야에서 사용 가능하다. 이러한 마이크로 노즐은 대부분 기계적 절삭법을 이용하여 알루미늄으로 만들어져왔다. 하지만 알루미늄으로 만들어진 마이크로 노즐은 경도가 낮아 세라믹 나노 입자를 적층하는 것에 적절치 못하며 사용가능한 수명이 짧다는 단점을 가지고 있다. 또한 가장 큰 단점으로 노즐목을 1mm이하로 제작하는 것이 어렵다는 것이다. 따라서 본 연구에서는 Si wafer를 Deep RIE 방식을 이용하여 3차원적으로 제작하였다. Deep RIE 방식 중 BOSCH process를 이용하였다. 이렇게 만들어진 마이크로 노즐은 다이렉트 프린팅 방식중 하나인 NPDS에 적용하였다. Si wafer로 만들어진 마이크로 노즐이 적용된 NPDS를 이용하여 graphite 분말을 가속하여 적층 실험을 실시하였다 이와 함께 전산 유체 역학(CFD)를 이용하여 마이크로 노즐일 이용한 초음속 가속 가능 여부를 판단하였다. 전산 유체 역학은 유한 요소법을 이용하여 유체의 거동을 시뮬레이션을 통하여 예측하는 것으로 마이크로 노즐 내에서 유체의 흐름을 예상할 수 있다. 실제 실험의 결과와 전산 유체 역학을 이용한 시뮬레이션 결과dml 비교 분석을 실시하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.5
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• pp.1-14
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• 2015

In case of a gas turbine engine for supersonic operation, the engine have a wide range of operating inlet mass flow rate and required high performance such as thrust and fuel consumption. Therefore, variable system and its optimal control logic are essentially needed. In this work, a method for performance prediction of a gas turbine engine with variable system compressor and its control scheme were developed. Conceptual design of compact acuation system for the operation of the variable system was also conducted. The performance of a low-bypass ratio mixed flow turbofan engine was analyzed, and it was observed that the surge margin of the engine is improved at off-design condition by applying the control scheme.